Federal Register / Vol. 77, No. 153 / Wednesday, August 8, 2012 / Rules and Regulations 47273 

Instructions of Boeing Alert Service Bulletin 

747–53A2507, Revision 1, dated January 14, 

2010. Doing the modification required by 

paragraph (p) of this AD terminates the onetime inspection requirements in this 

paragraph. 

(o) New Exception to Boeing Alert Service 

Bulletin 747–53A2507, Revision 1, Dated 

January 14, 2010 

Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2507, 

Revision 1, dated January 14, 2010, specifies 

a compliance time relative to ‘‘the Revision 

1 date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(p) New Modification 

Except as provided by paragraphs (p)(1) 

and (p)(2) of this AD: At the applicable times 

specified in paragraph 1.E, ‘‘Compliance,’’ of 

Boeing Service Bulletin 747–53A2559, 

Revision 1, dated August 4, 2011, modify the 

frame-to-tension-tie joints at body stations 

(STA) 1120 through 1220; do all related 

investigative and applicable corrective 

actions; do the repetitive post-modification 

detailed inspections for cracking of the 

tension tie and frame structure and all 

applicable corrective actions; and do the 

additional modification. Do all actions in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2559, Revision 1, dated August 4, 2011. 

Modifying the frame-to-tension-tie joints at 

body stations 1120 through 1220 terminates 

the repetitive inspection requirements of 

paragraphs (g) and (j) of this AD, the 

inspection requirements of paragraph (l) of 

this AD, and the one-time inspection 

requirements of paragraph (n) of this AD. 

(1) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 747–53A2559, 

Revision 1, dated August 4, 2011, specifies a 

compliance time relative to ‘‘the original 

issue date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Service Bulletin 747– 

53A2559, Revision 1, dated August 4, 2011, 

specifies to contact Boeing for repair 

instructions or additional modification 

requirements: Before further flight, repair the 

cracking or do the additional actions using a 

method approved in accordance with the 

procedures specified in paragraph (r) of this 

AD. 

(q) New Credit for Previous Actions 

This paragraph provides credit for the 

corresponding actions required by this AD, if 

those actions were done before the effective 

date of this AD using Boeing Alert Service 

Bulletin 747–53A2559, dated January 8, 

2009. 

(r) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 2007–23–18, 

Amendment 39–15266 (72 FR 65655, 

November 23, 2007), are approved as AMOCs 

for the corresponding requirements of 

paragraphs (g), (h), (i), and (j) of this AD. 

(5) AMOCs approved previously in 

accordance with AD 2007–23–18, 

Amendment 39–15266 (72 FR 65655, 

November 23, 2007), as a terminating action, 

are approved as AMOCs for the requirements 

of paragraph (p) of this AD. 

(s) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, Washington 

98057–3356; phone: (425) 917–6428; fax: 

(425) 917–6590; email: 

nathan.p.weigand@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https:// 

www.myboeingfleet.com. 

(3) You may review copies of the 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(t) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 747– 

53A2507, Revision 1, dated January 14, 2010. 

(ii) Boeing Service Bulletin 747–53A2559, 

Revision 1, dated August 4, 2011. 

(3) The following service information was 

approved for IBR on November 28, 2007 (72 

FR 65655, November 23, 2007): 

(i) Boeing Alert Service Bulletin 747– 

53A2507, dated April 21, 2005. 

(ii) Reserved. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https:// 

www.myboeingfleet.com. 

(3) You may review copies of the 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr_locations.html. 

Issued in Renton, Washington, on July 23, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–18627 Filed 8–7–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0264; Directorate 

Identifier 2011–NM–179–AD; Amendment 

39–17147; AD 2012–15–17] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A300 B4–603, B4–605R, 

and B4–622R airplanes; Model A300 

C4–605R Variant F airplanes; and Model 

A300 F4–600R series airplanes. This AD 

was prompted by a report that chafing 

was detected between the autopilot 

electrical wiring conduit and the wing 

bottom skin. This AD requires 

modifying the wiring installation on the 

right-hand wing. We are issuing this AD 

to prevent sparking due to electrical 

chafing when flammable vapors are 

present in the area, which could cause 

an uncontrolled fire. 


wreier-aviles on DSK5TPTVN1PROD with RULES
47274 Federal Register / Vol. 77, No. 153 / Wednesday, August 8, 2012 / Rules and Regulations 

DATES: This AD becomes effective 

September 12, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 12, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–2125; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on March 15, 2012 (77 FR 

15291). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During a scheduled general visual 

inspection in a zone adjacent to a fuel tank 

(zone 675) chafing was detected between the 

autopilot electrical wiring conduit and the 

wing bottom skin. 

This condition, in the scope of published 

FAA SFAR88 [Special Federal Aviation 

Regulation] and JAA [Joint Aviation 

Authority] Internal Policy INT/POL/25/12, is 

considered on ground to be a potential source 

of explosive condition due to the risk of a 

spark with electrical wire chafing when 

flammable vapours are present in the area. If 

left uncorrected, this condition could lead to 

an uncontrolled fire. 

For the reasons described above, this 

[EASA] AD requires modification of the 

wiring installation to improve the routing 

and the protection of the harnesses in the 

zone 675/Rib 6 of the Right Hand wing. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Request To Extend the Compliance 

Time 

UPS requested that we extend the 

proposed compliance time. The NPRM 

(77 FR 15291, March 15, 2012) proposed 

a compliance time of ‘‘within 30 months 

or 4,500 flight hours after the effective 

date of this AD,’’ for modifying the 

wiring in zone 675 of the right-hand 

wing. UPS stated that extending the 

compliance time to ‘‘within 40 months 

or 4,500 flight hours after the effective 

date of this AD,’’ would allow it to 

accomplish the required actions at its 

heavy maintenance facility during Ccheck visits. UPS stated that the line 

maintenance environment is not 

conducive to this type of work due to 

the required ground time, labor, and 

other resources, which are available at 

its major maintenance facility. UPS 

stated that its current maintenance 

program is based on a 30-month C-check 

interval. UPS also stated that in order to 

accommodate this modification at Ccheck in its major maintenance facility, 

it will need an additional 10 months to 

allow for planning and preparations, 

including developing engineering 

orders, prototyping, obtaining necessary 

management and finance approvals, 

parts acquisition, and parts lead-time. 

We do not agree to extend the 

compliance time specified in this final 

rule. In developing an appropriate 

compliance time for this action, we 

considered the urgency associated with 

the subject unsafe condition, the 

manufacturer’s recommendations, the 

availability of required parts, and the 

practical aspect of accomplishing the 

required modification within a period of 

time that corresponds to the normal 

scheduled maintenance for most 

affected operators. Under the provisions 

of paragraph (h)(1) of the final rule, we 

will consider requests for approval of an 

extension of the compliance time if 

sufficient data are submitted to 

substantiate that the new compliance 

time would provide an acceptable level 

of safety. We have not changed the AD 

in this regard. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

132 products of U.S. registry. We also 

estimate that it will take about 7 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $1,720 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$305,580, or $2,315 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM (77 FR 15291, 

March 15, 2012), the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 77, No. 153 / Wednesday, August 8, 2012 / Rules and Regulations 47275 

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2012–15–17 Airbus: Amendment 39–17147. 

Docket No. FAA–2012–0264; Directorate 

Identifier 2011–NM–179–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 12, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

603, B4–605R, and B4–622R airplanes; Model 

A300 C4–605R Variant F airplanes; and 

Model A300 F4–605R and F4–622R 

airplanes; certificated in any category; all 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 92. 

(e) Reason 

This AD was prompted by a report that 

chafing was detected between the autopilot 

electrical wiring conduit and the wing 

bottom skin. We are issuing this AD to 

prevent sparking due to electrical chafing 

when flammable vapors are present in the 

area, which could cause an uncontrollable 

fire. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Modification 

Within 30 months or 4,500 flight hours 

after the effective date of this AD, whichever 

occurs first: Modify the wiring in zone 675 

of the right-hand wing, in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–24–6109, 

dated July 4, 2011. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–2125; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC–REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(i) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2011–0161, 

dated August 26, 2011; and Airbus 

Mandatory Service Bulletin A300–24–6109, 

dated July 4, 2011; for related information. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Airbus Mandatory Service Bulletin 

A300–24–6109, dated July 4, 2011. 

(3) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(5) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on July 25, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–18884 Filed 8–7–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0598; Directorate 

Identifier 2012–CE–017–AD; Amendment; 

39–17150; AD 2012–16–03] 

RIN 2120–AA64 

Airworthiness Directives; HPH s. r.o. 

Sailplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all HPH 

s. r.o. Models 304C, 304CZ, and 304CZ– 

17 sailplanes. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by an 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. The MCAI 

describes the unsafe condition as the 

lack of a drain hole in the elevator 

control rod, which may allow water to 

accumulate in the control rod and lead 

to possible corrosion. This condition 

could cause the elevator control rod to 

fail, which could result in loss of 

control of the sailplane. We are issuing 

this AD to require actions to address the 

unsafe condition on these products. 

DATES: This AD is effective September 

12, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of September 12, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

For service information identified in 

this AD, contact HPH spol. s. r.o., 

Cˇ a ́slavska ́ 126, P.O. Box 112, 284 01 

Kutna ́ Hora, Czech Republic; phone: 

+420 327 512 633; fax: +420 327 513 

441; email: hph@hph.cz; Internet: 

www.hph.cz. You may review copies of 


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